CN102837819A - Wing surface increased flow short distance takeoff and landing carrier-based airplane - Google Patents
Wing surface increased flow short distance takeoff and landing carrier-based airplane Download PDFInfo
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- CN102837819A CN102837819A CN 201210277195 CN201210277195A CN102837819A CN 102837819 A CN102837819 A CN 102837819A CN 201210277195 CN201210277195 CN 201210277195 CN 201210277195 A CN201210277195 A CN 201210277195A CN 102837819 A CN102837819 A CN 102837819A
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- air nozzle
- screw propeller
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Abstract
The invention provides a wing surface increased flow short distance takeoff and landing carrier-based airplane, and belongs to a propeller-driven aircraft or a jet aircraft. Strong airflow produced by propellers or a jet engine blows over wings toward back, meaning that air velocity over the wings is accelerated by the propellers or the jet engine to make the air velocity over the wings greater, the pressure lower and pressure difference above and below the wings larger, so that lift force received by the airplane is bigger; the airplane can climb higher without horizontal acceleration; takeoff distance is shortened; and even the airplane can take off and land vertically and steadily. The airplane can fly faster under the condition of no upward climbing.
Description
Technical field the invention belongs to the jet plane technical field
Background technology
Current jet plane must have sufficiently long special-purpose airfield runway to supply its landing, perhaps must launch or jetting system, and landing on the small-sized island of incompatibility.Helicopter flight speed and highly lower.VTOL class jet plane technical risk is bigger, and load carrying ability reduces greatly.Because more past high-altitude, air are thin more, under the driving engine equal-wattage situation, along with the rising of height, air is more little to the lift of aircraft, thereby the flying height of all above these aircrafts is all lower.
Summary of the invention
The present invention blows over the airflow that jet engine produces from the wing top backward; Be the air rate that driving engine quickens the wing top, make the flow velocity of wing top air bigger, pressure is lower; Difference of pressure is bigger up and down for wing, and the lift that aircraft receives is also just bigger.
Before taking off, the dead brake of stopping, elongation front-wheel support; Start the engine and open the throttle wide, the air rate of wing top be just greater than below air rate (the below flow velocity is about 0), and jet generation is in the time of the thrust of front upper place; Wing produces the lift to the back upper place, the horizontal component of force partial offset of the two.Aircraft just had been subjected to the lift that makes progress before motion.So the takeoff runway of aircraft shortens greatly; Even (slightly hour its ascent direction might not vertical ground though when engine power to reach standing start; But can VTOL when engine power is big, even, engine power takes off) when enough falling back greatly the time.
After taking off, reduce the head inclination angle through elevating rudder, fuselage and horizontal plane angle are reduced, this moment, engine-horizontal thrust was maximum, had accelerated horizontal velocity.
Because in the flight course, driving engine is accelerated the air rate of wing top, and lift is more powerful, so any aircraft of height in existing use of creeping.
During brake, head is mentioned, jet thrust and wing to the front upper place offset part of horizontal power to the lift of back upper place, and horizontal velocity reduces.Even can hover (just this moment head obliquely).
During landing, on the basis of above-mentioned brake, reduce engine throttle, make jet generation to the lift combined action to the back upper place of front upper place power and wing, its level of making a concerted effort is offset, and vertically addition reaches aircraft weight, the aircraft grease it in.Trailing wheel lands earlier.
Description of drawings
Fig. 1---whole stereo appearance figure
Fig. 2---wing lateral plan
---wing 2---air nozzle 3---fuselage 4---empennage 5---elevating rudder 6---admission port wherein: 1
The specific embodiment
This invention power pack section can have following three kinds of situation:
1. driving engine can be the jet engine that is built in both sides wing (1) interior forward end; At least one driving engine of every side (can be that a plurality of puffers slightly are arranged in a row); Bilateral symmetry is placed; Driving engine sucks fresh air by admission port (6), and exhausr port is positioned at the air nozzle (2) of wing (1) upper front part.
2. driving engine also can place wing (1) outside the place ahead fuselage (3) both sides; Left-right symmetric; Through conduit high temperature and high pressure gas is inserted the admission port (6) in wing (1) the place ahead, from air nozzle (2) ejection, perhaps driving engine places fuselage (3) up and down or fuselage (3) inside; Through conduit high temperature and high pressure gas is inserted the admission port (6) in wing (1) the place ahead, spray from air nozzle (2).
3. the power pack section of this invention can also be the screw propeller that places above-mentioned three kinds of said positions of situation, by the engine drive screw propeller, makes air get into wing by admission port (6), sprays from air nozzle (2).
Operating process is following:
1. before taking off; Stop and extremely brake, elongation front-wheel support, start the engine and open the throttle wide; The air rate of wing (1) top is just greater than below air rate (the below flow velocity is about 0); Jet generation is in the time of the thrust of front upper place, and wing (1) produces the lift to the back upper place, the horizontal component of force partial offset of the two.Aircraft just had been subjected to the lift that makes progress before motion.So the takeoff runway of aircraft shortens greatly, even reach standing start (though its ascent direction might not vertically).
2. after taking off, through the inclination angle that elevating rudder (5) reduce fuselage (3), fuselage (3) and horizontal plane angle are reduced, this moment, engine-horizontal thrust was maximum, had accelerated horizontal velocity.
3. because in the flight course, driving engine is accelerated the air rate of wing (1) top, and lift is more powerful, so any aircraft of height in existing use of creeping.
4. when braking, head is mentioned, jet thrust and wing (1) to the front upper place offset part of horizontal power to the lift of back upper place, and horizontal velocity reduces.Even can hover (just this moment head obliquely).
5. when landing, on the basis of above-mentioned brake, reduce engine throttle, make jet generation produce the lift combined action to the back upper place to the power and the wing (1) of front upper place, its level of making a concerted effort is offset, and vertically addition reaches aircraft weight, the aircraft grease it in.Trailing wheel lands earlier.
Claims (5)
1. wing spray carrier-borne aircraft drives screw propeller by jet engine or rotary engine and forms its power system, it is characterized in that; In wing the place ahead, opening admission port (6) is forward arranged, back in admission port (6); The top of wing; Opening direction air nozzle (2) is backward arranged, and the air-flow that the jet or screw propeller of driving engine produces is finally sprayed by the air nozzle (2) of wing (1) front upper backward, and gaseous blast is through upper surface of the airfoil.
2. according to the spray of the wing under the claim 1 carrier-borne aircraft, can drive, it is characterized in that by jet engine; Jet engine is built in both sides wing (1) interior forward end; Place between admission port (6) and the air nozzle (2), at least one driving engine of every side (can be that a plurality of puffers slightly are arranged in a row), bilateral symmetry is placed; Driving engine sucks fresh air by admission port (6), and high-temperature high-pressure fuel gas is discharged outside the body by air nozzle (2).
3. according to the spray of the wing under the claim 1 carrier-borne aircraft; Can drive by jet engine; Jet engine is placed on wing (1); It is characterized in that, be closed pipeline between admission port (6) and air nozzle (2), with other conduit the air extractor duct of jet engine led to the airtight gas of admission port (6) that is positioned at the wing front end to connect; The high-temperature high-pressure fuel gas that jet engine produces is got into by the admission port (6) that places wing (1) front end, then by being positioned at anterior top air nozzle (2) ejection of wing (1).
4. according to the spray of the wing under the claim 1 carrier-borne aircraft, can drive, it is characterized in that by screw propeller; The screw propeller position is to be built in both sides wing (1) front end inside; Place between admission port (6) and the air nozzle (2), at least one screw propeller of every side (can be that a plurality of oars of minor spiral slightly are arranged in a row), bilateral symmetry is placed; By admission port (6) aspirated air, discharge outside the body by air nozzle (2).
5. according to the spray of the wing under the claim 1 carrier-borne aircraft; Can be driven by screw propeller, screw propeller is placed on wing (1), it is characterized in that; Between admission port (6) and air nozzle (2) is closed pipeline; With other conduit the air extractor duct of screw propeller is led to the airtight gas of admission port (6) that is positioned at the wing front end and to connect, the high pressure air that screw propeller produces is got into by the admission port (6) that places wing (1) front end, then by being positioned at air nozzle (2) ejection of wing (1) above anterior.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201210277195 CN102837819A (en) | 2012-07-22 | 2012-07-22 | Wing surface increased flow short distance takeoff and landing carrier-based airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201210277195 CN102837819A (en) | 2012-07-22 | 2012-07-22 | Wing surface increased flow short distance takeoff and landing carrier-based airplane |
Publications (1)
| Publication Number | Publication Date |
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| CN102837819A true CN102837819A (en) | 2012-12-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN 201210277195 Pending CN102837819A (en) | 2012-07-22 | 2012-07-22 | Wing surface increased flow short distance takeoff and landing carrier-based airplane |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106902519A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of ejection type soaring plane model |
| CN106902522A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of wing for being applied to ejection type soaring aeroplane model |
| CN106902518A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of step wing for ejection type soaring aeroplane model |
| CN106914021A (en) * | 2016-10-30 | 2017-07-04 | 天津师范大学 | A kind of ejection type soaring aeroplane model |
| CN109606702A (en) * | 2018-12-03 | 2019-04-12 | 江西洪都航空工业集团有限责任公司 | A kind of transporter short take-off and landing system |
| CN113928536A (en) * | 2021-11-05 | 2022-01-14 | 北京航空航天大学 | Method for reducing intensity of infrared radiation signal of hypersonic aircraft |
-
2012
- 2012-07-22 CN CN 201210277195 patent/CN102837819A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106902519A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of ejection type soaring plane model |
| CN106902522A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of wing for being applied to ejection type soaring aeroplane model |
| CN106902518A (en) * | 2016-10-30 | 2017-06-30 | 天津师范大学 | A kind of step wing for ejection type soaring aeroplane model |
| CN106914021A (en) * | 2016-10-30 | 2017-07-04 | 天津师范大学 | A kind of ejection type soaring aeroplane model |
| CN106902519B (en) * | 2016-10-30 | 2023-03-28 | 天津师范大学 | Ejection type gliding aircraft model |
| CN109606702A (en) * | 2018-12-03 | 2019-04-12 | 江西洪都航空工业集团有限责任公司 | A kind of transporter short take-off and landing system |
| CN113928536A (en) * | 2021-11-05 | 2022-01-14 | 北京航空航天大学 | Method for reducing intensity of infrared radiation signal of hypersonic aircraft |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20121226 |